Recoatable exhaust liner cooling arrangement

Abstract

A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.

What is claimed is: 
     
       1. A gas turbine engine comprising:
 an exhaust liner including axially adjoining hot sheets radially spaced from one another at a joint that provides cooling slots arranged radially between the adjoining hot sheets; 
 a cold sheet spaced radially outwardly from the hot sheets and connected to at least one of the hot sheets by a band arranged in a cavity secured between the hot and cold sheets, wherein the hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space, the slots are arranged radially between the portions; 
 wherein the hot sheets provide first and second hot sheets each having first and second end portions, first end portion of the first hot sheet arranged radially outwardly of the second end portion of the second hot sheet; and 
 wherein a portion of the band is secured at the joint in a location in which the first and second end portions respectively of the first and second hot sheets axially overlap, and the band is discrete from either the hot sheets or the cold sheet. 
 
     
     
       2. The gas turbine engine according to  claim 1 , wherein the hot sheets are connected to the band at the joint. 
     
     
       3. The gas turbine engine according to  claim 2 , comprising an outer duct spaced radially outwardly from the cold sheet and forming a bypass flow passage there between, the cold sheets including cooling apertures fluidly interconnecting the bypass flow passage with the cavity for supplying cooling fluid to the slots. 
     
     
       4. The gas turbine engine according to  claim 3 , comprising a core exhaust passage arranged centrally within the hot sheets and axially downstream from turbines, the slots for providing the cooling fluid to surfaces of the hot sheets facing the core exhaust passage. 
     
     
       5. The gas turbine engine according to  claim 1 , wherein the slots are arranged radially between the first and second end portions. 
     
     
       6. The gas turbine engine according to  claim 5 , wherein spacers are arranged radially between the first and second end portions, the slots provided circumferentially between the spacers. 
     
     
       7. The gas turbine engine according to  claim 6 , wherein the portion of the band is arranged radially between the first and second end portions, the first and second end portions, spacers and portion of the band secured to one another in a radially overlapping relationship. 
     
     
       8. The gas turbine engine according to  claim 3 , wherein the band includes a bend extending radially inwardly from the cold sheet and axially away from a turbine section, the bend configured to direct the cooling flow from the cooling apertures to the slots. 
     
     
       9. The gas turbine engine according to  claim 6 , wherein the spacers are discrete from at least one of the first and second end portions. 
     
     
       10. The gas turbine engine according to  claim 6 , wherein the spacers are discrete from the band.